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HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il)
Reynolds number: 500,000
Max Cl/Cd: 78.93 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2010-il-500000-n5.txt
Download as CSV file: xf-hq2010-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7164   0.04154   0.03899  -0.0587   1.0000   0.0041
 -10.000  -0.7313   0.03701   0.03417  -0.0582   1.0000   0.0041
  -9.750  -0.7435   0.03226   0.02901  -0.0566   1.0000   0.0041
  -9.500  -0.7350   0.03059   0.02720  -0.0553   1.0000   0.0043
  -9.250  -0.7212   0.02782   0.02411  -0.0555   0.9969   0.0044
  -9.000  -0.6963   0.02559   0.02161  -0.0571   0.9903   0.0045
  -8.750  -0.6689   0.02346   0.01918  -0.0588   0.9852   0.0048
  -8.500  -0.6422   0.02153   0.01695  -0.0601   0.9791   0.0050
  -8.250  -0.6124   0.02021   0.01541  -0.0614   0.9736   0.0054
  -8.000  -0.5839   0.01894   0.01391  -0.0624   0.9669   0.0058
  -7.750  -0.5540   0.01798   0.01273  -0.0634   0.9601   0.0062
  -7.500  -0.5264   0.01672   0.01125  -0.0639   0.9517   0.0065
  -7.250  -0.4995   0.01530   0.00964  -0.0644   0.9431   0.0070
  -7.000  -0.4729   0.01452   0.00876  -0.0645   0.9332   0.0074
  -6.750  -0.4463   0.01390   0.00803  -0.0645   0.9240   0.0079
  -6.500  -0.4201   0.01329   0.00730  -0.0643   0.9153   0.0085
  -6.250  -0.3945   0.01273   0.00663  -0.0640   0.9063   0.0090
  -6.000  -0.3686   0.01229   0.00606  -0.0637   0.8981   0.0097
  -5.750  -0.3434   0.01172   0.00538  -0.0633   0.8894   0.0109
  -5.500  -0.3177   0.01129   0.00489  -0.0629   0.8804   0.0122
  -5.250  -0.2916   0.01095   0.00445  -0.0626   0.8722   0.0136
  -5.000  -0.2653   0.01062   0.00404  -0.0623   0.8643   0.0155
  -4.750  -0.2388   0.01029   0.00369  -0.0621   0.8579   0.0204
  -4.500  -0.2121   0.01002   0.00341  -0.0619   0.8514   0.0283
  -4.000  -0.1579   0.00960   0.00294  -0.0617   0.8396   0.0416
  -3.750  -0.1307   0.00941   0.00273  -0.0616   0.8336   0.0494
  -3.500  -0.1036   0.00919   0.00253  -0.0615   0.8275   0.0626
  -3.250  -0.0765   0.00896   0.00233  -0.0614   0.8210   0.0827
  -3.000  -0.0494   0.00871   0.00215  -0.0613   0.8148   0.1107
  -2.750  -0.0227   0.00840   0.00198  -0.0613   0.8078   0.1583
  -2.250   0.0306   0.00770   0.00165  -0.0612   0.7939   0.2908
  -2.000   0.0566   0.00725   0.00151  -0.0611   0.7867   0.3957
  -1.750   0.0830   0.00695   0.00144  -0.0609   0.7784   0.4789
  -1.500   0.1095   0.00675   0.00141  -0.0606   0.7686   0.5455
  -1.250   0.1364   0.00667   0.00138  -0.0603   0.7574   0.5853
  -1.000   0.1632   0.00661   0.00137  -0.0600   0.7453   0.6228
  -0.500   0.2177   0.00659   0.00134  -0.0595   0.7216   0.6636
  -0.250   0.2451   0.00661   0.00133  -0.0593   0.7089   0.6779
   0.000   0.2723   0.00662   0.00134  -0.0591   0.6966   0.6933
   0.250   0.2996   0.00664   0.00135  -0.0589   0.6842   0.7078
   0.500   0.3269   0.00669   0.00136  -0.0587   0.6700   0.7184
   0.750   0.3542   0.00673   0.00137  -0.0585   0.6564   0.7265
   1.000   0.3817   0.00678   0.00140  -0.0584   0.6442   0.7348
   1.250   0.4089   0.00683   0.00144  -0.0582   0.6304   0.7435
   1.500   0.4360   0.00690   0.00148  -0.0580   0.6144   0.7522
   2.000   0.4896   0.00707   0.00159  -0.0575   0.5793   0.7708
   2.250   0.5161   0.00719   0.00168  -0.0572   0.5565   0.7805
   2.500   0.5421   0.00733   0.00176  -0.0569   0.5317   0.7908
   2.750   0.5678   0.00750   0.00187  -0.0564   0.5043   0.8017
   3.000   0.5928   0.00771   0.00201  -0.0559   0.4673   0.8133
   3.250   0.6165   0.00803   0.00217  -0.0552   0.4193   0.8262
   3.500   0.6403   0.00835   0.00237  -0.0545   0.3786   0.8408
   3.750   0.6633   0.00870   0.00258  -0.0537   0.3307   0.8582
   4.000   0.6851   0.00908   0.00282  -0.0526   0.2844   0.8834
   4.250   0.7119   0.00934   0.00306  -0.0525   0.2533   0.9344
   4.500   0.7465   0.00958   0.00328  -0.0542   0.2361   1.0000
   4.750   0.7724   0.00983   0.00349  -0.0540   0.2232   1.0000
   5.000   0.7980   0.01011   0.00371  -0.0537   0.2067   1.0000
   5.250   0.8230   0.01043   0.00398  -0.0534   0.1869   1.0000
   5.500   0.8474   0.01082   0.00425  -0.0530   0.1595   1.0000
   5.750   0.8694   0.01146   0.00463  -0.0523   0.1131   1.0000
   6.000   0.8917   0.01207   0.00506  -0.0516   0.0815   1.0000
   6.250   0.9153   0.01253   0.00544  -0.0510   0.0650   1.0000
   6.500   0.9389   0.01298   0.00586  -0.0505   0.0522   1.0000
   6.750   0.9622   0.01345   0.00627  -0.0499   0.0410   1.0000
   7.000   0.9856   0.01389   0.00668  -0.0493   0.0340   1.0000
   7.250   1.0096   0.01427   0.00708  -0.0488   0.0296   1.0000
   7.500   1.0323   0.01476   0.00754  -0.0482   0.0227   1.0000
   7.750   1.0551   0.01523   0.00800  -0.0475   0.0172   1.0000
   8.000   1.0769   0.01579   0.00857  -0.0467   0.0109   1.0000
   8.250   1.0973   0.01649   0.00925  -0.0458   0.0058   1.0000
   8.500   1.1179   0.01715   0.00994  -0.0448   0.0047   1.0000
   8.750   1.1384   0.01779   0.01065  -0.0437   0.0040   1.0000
   9.000   1.1587   0.01841   0.01136  -0.0427   0.0037   1.0000
   9.250   1.1783   0.01907   0.01211  -0.0417   0.0034   1.0000
   9.500   1.1967   0.01982   0.01296  -0.0404   0.0032   1.0000
   9.750   1.2146   0.02056   0.01380  -0.0391   0.0031   1.0000
  10.000   1.2311   0.02138   0.01476  -0.0376   0.0030   1.0000
  10.250   1.2463   0.02226   0.01574  -0.0360   0.0029   1.0000
  10.500   1.2577   0.02324   0.01684  -0.0338   0.0027   1.0000
  10.750   1.2661   0.02434   0.01805  -0.0312   0.0026   1.0000
  11.000   1.2736   0.02549   0.01932  -0.0287   0.0026   1.0000
  11.250   1.2776   0.02691   0.02088  -0.0260   0.0025   1.0000
  11.500   1.2760   0.02881   0.02294  -0.0230   0.0023   1.0000
  11.750   1.2817   0.03022   0.02448  -0.0211   0.0023   1.0000
  12.000   1.2853   0.03187   0.02626  -0.0192   0.0023   1.0000
  12.250   1.2882   0.03365   0.02817  -0.0176   0.0023   1.0000
  12.500   1.2887   0.03575   0.03041  -0.0161   0.0022   1.0000
  12.750   1.2887   0.03799   0.03279  -0.0149   0.0022   1.0000
  13.000   1.2880   0.04047   0.03543  -0.0140   0.0022   1.0000
  13.250   1.2843   0.04339   0.03854  -0.0134   0.0021   1.0000
  13.500   1.2806   0.04647   0.04176  -0.0132   0.0021   1.0000
  13.750   1.2740   0.05014   0.04559  -0.0135   0.0021   1.0000
  14.000   1.2665   0.05415   0.04977  -0.0142   0.0021   1.0000
  14.250   1.2572   0.05870   0.05448  -0.0156   0.0021   1.0000
  14.500   1.2467   0.06376   0.05970  -0.0175   0.0021   1.0000
  14.750   1.2341   0.06955   0.06566  -0.0201   0.0021   1.0000
  15.000   1.2212   0.07585   0.07212  -0.0233   0.0021   1.0000
  15.250   1.2047   0.08326   0.07971  -0.0273   0.0021   1.0000
  15.500   1.1891   0.09097   0.08758  -0.0316   0.0021   1.0000
  15.750   1.1728   0.09908   0.09583  -0.0362   0.0021   1.0000
  16.000   1.1548   0.10786   0.10477  -0.0412   0.0021   1.0000
  16.250   1.1375   0.11666   0.11369  -0.0462   0.0021   1.0000
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